公开(公告)号：US07452183B2

公开(公告)日：2008-11-18

申请号：US11161517

申请日：2005-08-06

Applicant: Michael Anthony Ruthemeyer ,  Glenn Herbert Nichols ,  Ching-Pang Lee

Inventor： Michael Anthony Ruthemeyer ,  Glenn Herbert Nichols ,  Ching-Pang Lee

IPC: F01D11/08

CPC classification number: F01D11/005 ,  F01D25/246

Abstract: A shroud assembly is provided for a gas turbine engine having a temperature at a hot operating condition substantially greater than at a cold assembly condition thereof. The shroud assembly includes at least one arcuate shroud segment adapted to surround a row of rotating turbine blades. The shroud segment has an arcuate, axially extending mounting flange. A shroud hanger includes an arcuate, axially-extending hook. A dimension of one of the shroud segments and the shroud hanger are selected to produce a preselected dimensional relationship therebetween at the hot operating condition.

Abstract translation: 提供了一种用于燃气涡轮发动机的护罩组件，其具有基本上大于其冷组装状态的热操作状态下的温度。 护罩组件包括适于包围一排旋转涡轮叶片的至少一个弓形护罩段。 护罩段具有弓形的轴向延伸的安装凸缘。 护罩悬挂器包括弓形的轴向延伸的钩。 选择护罩段和护罩悬挂器中的一个的尺寸以在热操作条件下产生其间的预选尺寸关系。

公开(公告)号：US20080281562A1

公开(公告)日：2008-11-13

申请号：US11747351

申请日：2007-05-11

Applicant: Chen-Yu Jack Chou ,  Ching-Pang Lee ,  David Charles Wisler

Inventor： Chen-Yu Jack Chou ,  Ching-Pang Lee ,  David Charles Wisler

IPC: G06F17/50 ,  G06G7/64 ,  G06G7/57 ,  G06G7/72

CPC classification number: G01M9/065 ,  B33Y80/00

Abstract: Methods for optimizing at least one operating parameter of an engine component using an experimentally measured 3D flow field involving providing a magnetic resonance imaging machine, providing a model of an engine component, placing the model into the magnetic resonance imaging machine with a fluid flow source for applying an external fluid flow, applying the external fluid flow to the model, collecting data related to the external fluid flow about the model, and optimizing at least one operating parameter of the component using the data.

Abstract translation: 使用实验测量的3D流场来优化发动机部件的至少一个操作参数的方法，包括提供磁共振成像机，提供发动机部件的模型，将所述模型放置在磁共振成像机中，所述流体流动源用于 施加外部流体流，将外部流体流施加到模型，收集与模型相关的外部流体流动的数据，以及使用该数据来优化组件的至少一个操作参数。

公开(公告)号：US07442004B2

公开(公告)日：2008-10-28

申请号：US11161518

申请日：2005-08-06

Applicant: Michael Anthony Ruthemeyer ,  Glenn Herbert Nichols ,  Ching-Pang Lee

Inventor： Michael Anthony Ruthemeyer ,  Glenn Herbert Nichols ,  Ching-Pang Lee

IPC: F01D11/08

CPC classification number: F01D9/04 ,  F05D2230/60 ,  F05D2240/11 ,  F05D2260/30 ,  F05D2260/941

Abstract: A C-clip for a gas turbine engine includes an arcuate outer arm having a first radius of curvature; an arcuate, inner arm having a second radius of curvature which is substantially greater than the first radius of curvature; and an arcuate extending flange connecting the outer and inner arms. The flange, the outer arm, and the inner arm collectively define a generally C-shaped cross-section. A shroud assembly includes a shroud segment with a mounting flange, and a shroud hanger with an arcuate hook disposed in mating relationship to the mounting flange. An arcuate C-clip having inner and outer arms overlaps the hook and the mounting flange. The shroud segment and the C-clip are subject to thermal expansion at the hot operating condition. A dimension of one of the shroud segment and the C-clip are selected to produce a preselected dimensional relationship therebetween at the hot operating condition.

Abstract translation: 用于燃气涡轮发动机的C形夹包括具有第一曲率半径的弓形外臂; 具有第二曲率半径的弓形内臂，其基本上大于所述第一曲率半径; 以及连接外臂和内臂的弓形延伸法兰。 凸缘，外臂和内臂共同地限定了大致C形的横截面。 护罩组件包括具有安装凸缘的护罩段和具有与安装法兰配合关系设置的弓形钩的护罩。 具有内臂和外臂的弧形C形夹与钩和安装法兰重叠。 护罩段和C形夹在热操作条件下经受热膨胀。 选择护罩段和C形夹之一的尺寸以在热操作条件下产生预定尺寸关系。

公开(公告)号：US20080206042A1

公开(公告)日：2008-08-28

申请号：US11565180

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Katherine Jaynetorrence Andersen

Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Katherine Jaynetorrence Andersen

IPC: F04D31/00

CPC classification number: F01D5/143 ,  F01D11/24 ,  F05D2240/11 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, circumferentially mixing the cooling air in a plenum defined within the leading edge to substantially uniformly distribute the cooling air throughout the gap, and directing the cooling air in the gap through at least one cooling hole formed between the plenum and the inner surface.

Abstract translation: 提供了一种用于冷却燃气涡轮发动机的护罩部分的方法。 该方法包括提供一种涡轮机护罩组件，其包括具有内表面和大致垂直于内表面的前缘的护罩区段，以及将涡轮喷嘴连接到涡轮机护罩区段，使得间隙限定在 涡轮喷嘴的外带和前缘。 该方法还包括将冷却空气引导到间隙中，将冷却空气周向地混合在限定在前缘内的增压室中，以将冷却空气基本上均匀地分布在整个间隙中，并且将空气中的冷却空气引导通过形成的至少一个冷却孔 在气室和内表面之间。

公开(公告)号：US20080152504A1

公开(公告)日：2008-06-26

申请号：US11615541

申请日：2006-12-22

Applicant: Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Craig Miller Kuhne

Inventor： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Craig Miller Kuhne

IPC: F01D9/00

CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D5/145 ,  Y02T50/673 ,  Y10T29/49321 ,  Y10T29/49323

Abstract: A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.

Abstract translation: 提供可用于发动机组件中的定子叶片。 定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处连接到第一侧壁。 翼型件还包括根部部分和尖端部分。 第一和第二侧壁都从根部延伸到尖端部分。 翼面根部形成为负的倾斜，并且翼型前端部形成为正的倾斜。

公开(公告)号：US20080145216A1

公开(公告)日：2008-06-19

申请号：US11642001

申请日：2006-12-19

Applicant: Kevin Samuel Klasing ,  Ching-Pang Lee ,  Scott David Hunter

Inventor： Kevin Samuel Klasing ,  Ching-Pang Lee ,  Scott David Hunter

IPC: F01D9/02 ,  F04D29/08

CPC classification number: F01D11/001 ,  F01D5/143 ,  F01D11/04 ,  Y02T50/673

Abstract: A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer and inner convex surfaces joined at a convex apex. The ovate ledge reduces aerodynamic losses at the rotary seal with a row of following turbine rotor blades.

Abstract translation: 涡轮级包括具有安装在内带和外带之间的一排叶片的定子喷嘴。 内带终止于从叶片向后收敛的卵形突出部，其中凸起的顶部与径向外部和内部凸起表面接合。 卵形凸缘在一系列以下的涡轮转子叶片上减小了在旋转密封处的空气动力学损失。

公开(公告)号：US20080135722A1

公开(公告)日：2008-06-12

申请号：US11609117

申请日：2006-12-11

Applicant: Hsin-Pang Wang ,  Marc Thomas Edgar ,  John Thomas Leman ,  Ching-Pang Lee ,  Eric Alan Estill

Inventor： Hsin-Pang Wang ,  Marc Thomas Edgar ,  John Thomas Leman ,  Ching-Pang Lee ,  Eric Alan Estill

IPC: B22C9/10 ,  B28B7/34

CPC classification number: B22C9/04 ,  B22C9/10 ,  C04B35/6269 ,  C04B2235/6026 ,  C04B2235/6028

Abstract: Disclosed herein is a method comprising injecting into a thin wall disposable core die a slurry having a viscosity of about 1 to about 1,000 Pascal-seconds at room temperature when tested at a shear rate of up to 70 seconds−1 and a flow index of less than 0.6 at a pressure of up to about 7 kilograms-force per square centimeter; wherein the thin wall disposable core die has an average wall thickness of about 1.5 to about 10 millimeters; curing the slurry to form a cured ceramic core; removing the thin wall disposable core die from the cured ceramic core; and firing the cured ceramic core to form a solidified ceramic core.

Abstract translation: 本文公开了一种方法，包括在室温下以至多70秒-1的剪切速率进行测试时，在室温下将具有约1至约1,000帕斯卡 - 秒的粘度的浆料注入薄壁一次性芯模中。 >，流量指数小于0.6，压力高达约7千克力/平方厘米; 其中所述薄壁一次性芯模的平均壁厚为约1.5至约10毫米; 固化浆料以形成固化的陶瓷芯; 从固化的陶瓷芯上去除薄壁一次性芯模; 并烧结固化的陶瓷芯以形成凝固的陶瓷芯。

公开(公告)号：US20080135721A1

公开(公告)日：2008-06-12

申请号：US11567409

申请日：2006-12-06

Applicant: Hsin-Pang Wang ,  John Thomas Leman ,  Thomas Francis McNulty ,  Ching-Pang Lee

Inventor： Hsin-Pang Wang ,  John Thomas Leman ,  Thomas Francis McNulty ,  Ching-Pang Lee

IPC: B22C9/10 ,  B22C1/22

CPC classification number: B22C1/183

Abstract: Disclosed herein is a method comprising disposing a casting composition within a sacrificial die; wherein internal features of the sacrificial die provide a replica of a desired casting; wherein the casting composition has a viscosity of about 1 to about 1,000 Pascal-seconds at room temperature when tested at a shear rate of up to 70 seconds−1; reacting the casting composition to form a gel matrix; removing the sacrificial die; extracting a solvent from the gel matrix to form a dried gel; and firing the dried gel to form a ceramic core. Disclosed herein too is a casting composition comprising a monomer and/or a polymer; and a metal and/or ceramic powder; wherein the casting composition has a viscosity of about 1 to about 1,000 Pascal-seconds at room temperature when tested at a shear rate of up to 70 seconds−1 and a flow index of less than 0.6.

Abstract translation: 本文公开了一种方法，包括在牺牲模具内设置浇铸组合物; 其中牺牲模具的内部特征提供所需铸件的复制品; 其中当在高达70秒-1的剪切速率下测试时，所述浇铸组合物在室温下具有约1至约1,000帕斯卡 - 秒的粘度; 使浇铸组合物反应形成凝胶基质; 去除牺牲模具; 从凝胶基质中提取溶剂以形成干凝胶; 并焙烧干燥的凝胶以形成陶瓷芯。 本文还公开了包含单体和/或聚合物的铸塑组合物; 和金属和/或陶瓷粉末; 其中当在高达70秒-1的剪切速率和小于0.6的流动指数下测试时，所述浇铸组合物在室温下具有约1至约1,000帕斯卡 - 秒的粘度。

公开(公告)号：US20080131263A1

公开(公告)日：2008-06-05

申请号：US11565472

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Verner Jones

Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Daniel Verner Jones

IPC: F01D5/08 ,  F01D5/22

CPC classification number: F01D11/08 ,  F01D11/10 ,  F05D2240/11 ,  F05D2260/202 ,  Y02T50/676

Abstract: A method for cooling a shroud segment of a gas turbine engine includes providing a turbine shroud assembly including a shroud segment having a leading edge defining a forward face. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face, wherein a lip formed on the aft face is positioned radially inwardly with respect to the gap and extends substantially axially downstream from the gap. Cooling air is directed into the gap. Cooling air exiting the gap impinges against the lip. Post impingement cooling air is directed at the forward face to facilitate forming a film cooling layer on the shroud segment. The film cooling layer is shielded from combustion gases flowing through the gas turbine engine.

Abstract translation: 一种用于冷却燃气涡轮发动机的护罩区段的方法包括提供一种涡轮机护罩组件，其包括具有限定前表面的前缘的护罩区段。 涡轮喷嘴联接到涡轮机护罩组件，使得在涡轮喷嘴的外带的前表面和前表面之间限定间隙，其中形成在后表面上的唇缘相对于间隙径向向内定位 并且从所述间隙基本轴向地延伸到下游。 冷却空气被引导到间隙中。 离开间隙的冷却空气撞击唇缘。 后冲击冷却空气指向前面，以便于在护罩段上形成薄膜冷却层。 膜冷却层与流过燃气涡轮发动机的燃烧气体屏蔽。

公开(公告)号：US20080128266A1

公开(公告)日：2008-06-05

申请号：US11606971

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

IPC: H05F3/00

CPC classification number: F01D5/186 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2270/172 ,  F15D1/12 ,  H05H1/2406 ,  Y02T50/673 ,  Y02T50/676 ,  Y10S415/914

Abstract: An upstream plasma boundary layer shielding system includes film cooling apertures disposed through a wall having cold and hot surfaces and angled in a downstream direction from a cold surface of the wall to an outer hot surface of the wall. A plasma generator located upstream of the film cooling apertures is used for producing a plasma extending downstream over the film cooling apertures. Each plasma generator includes inner and outer electrodes separated by a dielectric material disposed within a groove in the outer hot surface. The wall may be part of a hollow airfoil or an annular combustor or exhaust liner. A method for operating the upstream plasma boundary layer shielding system includes forming a plasma extending in the downstream direction over the film cooling apertures along the outer hot surface of the wall. The method may further include operating the plasma generator in steady state or unsteady modes.

Abstract translation: 上游等离子体边界层屏蔽系统包括通过具有冷和热表面的壁布置的薄膜冷却孔，并且在从壁的冷表面到壁的外部热表面的下游方向上成角度。 位于膜冷却孔的上游的等离子体发生器用于产生在膜冷却孔的下游延伸的等离子体。 每个等离子体发生器包括由设置在外部热表面中的凹槽内的电介质材料分开的内部和外部电极。 该壁可以是中空翼型件或环形燃烧器或排气衬套的一部分。 用于操作上游等离子体边界层屏蔽系统的方法包括形成沿着下游方向沿着壁的外部热表面在膜冷却孔上延伸的等离子体。 该方法还可以包括以等稳态或不稳定模式操作等离子体发生器。